Patent GB-1127856-A (GB)
Title: Improvements in or relating to power plants for aircraft
Inventor: BRITTEN COLIN GILLATT
IPC: F02C3/30
Filed: 1967-07-01
Abstract: 1,127,856. Gas turbine jet propulsion plant. ROLLS-ROYCE Ltd. July 1, 1967, No. 30457/67. Headings F1G and F1J An aircraft power plant comprises at least two gas turbine engines each having injection means whereby a power augmenting fluid may be injected into the gas flow through the engine, fluid-pressure operable valve means for controlling the flow of power augmenting fluid to the injection means, further control valve means to control the supply of pressure fluid to the fluid-pressure operable valve means and a device responsive to the torque produced by a shaft of the engine, the arrangement being such that, should one engine fail during operating of the power plant, a signal from the torque responsive device on that engine causes the further control valve means on the other engine to operate so as to open the fluid-pressure operable valve means on the other engine. The arrangement is described in a plant having two turbo-prop engines 1, 2, Fig. 1 each having a turbine 18 driving a centrifugal compressor 14, an autofeathering mechanism 30 or 30a for the propellor 24 and a water/methanol injection system 34 or 34a. Each feathering mechanism includes a torque responsive switch connected to the injection system of the other engine, i.e. a switch 31a, Fig.2, in mechanism 30a of engine 2 is connected to injection system 34 of engine 1 by cable 38 and vice versa. Each injection system includes a water/methanol tank 40, an electric pump 42, an electrically operated shut off cock 44 and a valve 46 to meter the flow of water/methanol through outlet 35 to injectors 36. Valve 46 includes a valve member 56 on the end of a rod carrying a piston 62 biased to the closed position by a spring 68. A conduit 72 can supply hydraulic fluid to the opposite side of piston 62 when a valve 74 opens as a predetermined engine speed is reached. A solenoid operated bleed valve 76 is mounted in conduit 72. When a three position selector switch 80, illustrated in the "off" position, is set in the "standby" position with wipers 82, 84 in contact with contacts 91, 94 respectively, coil 103 of a contactor 104 is energized to close contacts 106 and start pump 42. At the same time, the input 97 opens cock 44 to supply water/methanol to valve 46. However the coil 114 of bleed valve 76 is also energized via the contacts 116 of contactor 112 so that the valve 76 is held open to bleed off fluid from conduit 72 so that valve 46 remains closed. Should engine 2 now fail, the torque responsive switch 31a closes thereby energizing coil 118 to open contacts 116 and close contacts 117 thus de-energizing and short circuiting coil 114 so that bleed valve 76 closes. The hydraulic fluid-pressure thus opens valve 46 to allow the water/methanol to flow to augment the power of the remaining engine. The pressure of the water/ methanol in conduit 41 conduit 41 is monitored by an indicator lamp 49 operated by a pressure switch 48. In the event of an engine fire, movement of an emergency lever operates a micro-switch 100 to close the cock 44. The selector switch 80 has also an "on" position whereby the water/methanol is supplied irrespective of the position of the torque responsive switch 31a. The contactors 104, 112 may be replaced by transistor circuitry.